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研究生:吳宏佑
研究生(外文):Hom-Yu Wu
論文名稱:巡航用小型氣渦輪引擎之系統規劃與壓縮器流場之性能解析模擬研究
指導教授:賴正權夏筱明
學位類別:碩士
校院名稱:國防大學中正理工學院
系所名稱:兵器系統工程研究所
學門:軍警國防安全學門
學類:軍事學類
論文種類:學術論文
論文出版年:2004
畢業學年度:92
語文別:中文
中文關鍵詞:壓縮器性能圖流場逐級分析小型氣渦輪引擎軸流式壓縮器
外文關鍵詞:compressor maprow-by-row analysissmall turbofan engineaxial compressor
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鑒於氣渦輪引擎對促進航太工業與產業發展具有正向積極效益,及其在國防航太載具推進系統研發的重要性,本論文乃以一具小型氣渦輪引擎系統規劃及壓縮器流場分析為題,進行理論探討與模擬研究。在研究內容方面,首先依典型氣渦輪引擎系統模組的操作特性,進行其工作氣流性質變化的理論分析,根據基本的熱氣動力原理、質量及能量守恆定律、工作氣流及動力模組的操作匹配條件,以建立引擎系統規劃與性能計算的理論基礎。其次為針對文獻實例引擎進行廣泛的資料蒐集與參數綜整,並參酌近代渦輪引擎製造工藝水準的提升,訂定研究模擬的對象,並採用本團隊發展的CSJP-6計算程式,進行該引擎之設計點(Design Point)整合性能計算與各模組特徵參數值指配(Allocation),特別是壓縮模組之氣流量、壓縮比及壓縮效率等主要參數。最後則是根據這些經過引擎系統整合考量所指配的性能數據,進行壓縮器葉片流場的幾何條件訂定,並根據基本氣渦輪機原理(Principles of Turbomachinery)及二維葉片流場逐級分析(Cascade Analysis)方法,導出壓縮模組於不同操作條件下的性能計算理論架構,再應用Visual Basic程式語言設計出一套實用視窗軟體CSJP-8,作為模擬於指定規範下的壓縮器操作性能圖(Compressor Map)之用。綜合本論文主要研究成果:除完成一具小型渦輪引擎系統的熱氣動力特性規劃外,並應用基本的理論解析方法,發展一套軸流式壓縮器性能圖模擬軟體CSJP-8,且成功地以四級軸流式壓縮器為例,完成其操作性能圖的預測,及獲得壓縮器出口氣流壓力、溫度與氣流量,於不同轉速操作條件下之合理範圍值,當可作為其下游燃室模組設計的參考。由於本論文研究係以解析方法為主,故如何在壓縮器葉片流場之逐級分析過程中,將適合的壓力損耗模式(Loss Model)與三維效應評估算式納入,當可作為後續探討的主題。
In viewing its role in motivating the prosperity of regional aircrafts and leading to new design of defense propulsion systems, the study of a small gas turbine engine (SGTE) has caught a lot of attention, thus forming the subject of the present thesis. Focus has been placed on the airflow analysis, the design point and the compressor map for such an engine. In approach, a pipeline analysis for the engine airflow is conducted first, based on fundamental conservation laws and aerothermodynamics and the matching conditions for a steady, equilibrium engine operation. Governing equations for the flow property and the resultant engine performance were derived, serving as a basis for further code developments. Followed is a trial-and-error process, using a so-called CSJP-6 computer program by our Lab, to simulate the engine performance criterion determined from an extensive data survey of documented SGTE, with pertinent modifications by technology levels. Then is the determining of the compressor map based on the component spec obtained from using CSJP-6. A theoretical architecture for the cascade flow and performance calculation was set up, using a two-dimensional, row-by-row analysis method, and was used to develop a practical windows program, named CSJP-8, for the present C-map generation. In summary, the study of an SGTE has been successfully conducted in theories, with major results integrated in the CSJP-8 proposed here. Typical demonstration for the case of a four-stage, axial flow compressor is reported, with reasonable data of the total pressure, temperature and the flow rate at the compressor exit, which may serves as a reference for successive burner design works. It is noted that as an analytical approach, this thesis welcomes further correlations for the effect of the cascade diffusion losses as well as that due to the wake flow interactions, to make the C-map generation result more practical.
誌謝.........................................ii
摘要........................................iii
ABSTRACT.....................................iv
目錄..........................................v
表目錄......................................vii
圖目錄.....................................viii
符號說明......................................x
1. 緒論.......................................1
1.1 問題緣起..................................1
1.2 文獻探討..................................2
1.3 研究方法..................................4
1.4 論文架構..................................6
2. 小型氣渦輪引擎之系統規劃與模組分析.........8
2.1 實例探討與系統模組化......................9
2.2 主要模組特性參數分析.....................13
2.2.1 引擎進氣段.............................14
2.2.2 風扇與旁通段...........................15
2.2.3 壓縮段.................................16
2.2.4 燃室段.................................18
2.2.5 高壓渦輪段.............................19
2.2.6 低壓渦輪段.............................21
2.2.7 尾管與噴嘴段 .......................... 22
2.3 模組整合與引擎性能估算.................24
3. 小型氣渦輪引擎之系統規劃與性能模擬........29
3.1目標引擎系統規劃..........................29
3.2引擎系統性能模擬..........................32
3.3壓縮器性能圖概要..........................39
3.4壓縮器葉片幾何條件及氣動力參數值訂定......43
4. 目標引擎低壓壓縮器之流場性能解析與模擬....47
4.1 目標引擎低壓壓縮器流場逐級分析...........47
4.1.1 進氣導片流場 ...........................47
4.1.2 轉子葉片流場 ...........................49
4.1.3 定子葉片流場 ...........................54
4.2 目標引擎低壓壓縮器流場性能計算.........58
4.3 目標引擎低壓壓縮器性能圖繪製.............64
5. 結論......................................74
參考文獻.....................................77
自傳.........................................81
[1]http://www.itri.org.tw/chi/news_events/feature/2000/fe-0891201-p2.jsp
[2]Srinivasa, C., “Performance Analysis of a Mixed Flow Turbofan Engine at the Design Point,” Proc. of 9th Natl. Conf. on IC Engine and Comb., pp.19-22, Dehra Dun, India, 1985.
[3]Baig, M. F. and Saravanamutto, H. I. H., “Off-Design Performance Prediction of Single Spool Turbojets Using Gas Dynamics,” J. of Prop. & Power, Vol. 13, No. 6, pp. 808-810, 1997.
[4]夏筱明、茹承斌,“單軸渦噴引擎設計點熱動力循環建構之研究”,第七屆國防科技研討會論文集,中正理工學院,桃園大溪,1998。
[5]夏筱明、林豪傑,“雙軸氣渦輪機設計點操作循環之模擬研究”,1999中華民國「航太學會/燃燒學會/民航學會」航太學術聯合會議論文集,第689-695頁,中正理工學院,桃園大溪,1999。
[6]夏筱明、林豪傑,“混流式渦扇發動機設計點循環之模擬研究”,第九屆國防科技研討會論文集,第121-128頁,中正理工學院,桃園大溪,2000。
[7]夏筱明、林豪傑,“雙軸混流式渦扇發動機偏離設計點性能之模擬研究”,2001中華民國「燃燒學會/民航學會/航太學會」學術聯合會議論文集,第53-60頁,元智大學,桃園中壢,2001。
[8]夏筱明、賴正權、高廣權,“雙軸分流式渦扇發動機設計點性能之模擬研究”, 2001中華民國「燃燒學會/民航學會/航太學會」學術聯合會議論文集,第45-52頁,元智大學,桃園中壢,2001。
[9]夏筱明、高廣權,“雙軸分流式渦扇發動機偏離設計點性能之模擬研究”,2002中華民國「民航學會/航太學會/燃燒學會」學術聯合會議論文集,第705-712頁,國立高雄餐旅學院,高雄市,2002。
[10]夏筱明、潘彥良,“具齒輪式渦輪風扇噴射引擎設計點性能數據規範之重建”,2002中華民國「民航學會/航太學會/燃燒學會」學術聯合會議論文集,第381-388頁,國立高雄餐旅學院,高雄市,2002。
[11]Koenig, R. W. and Fisbbacb, L. H., GENENG--A Program for Calculating Design and Off-Design Performance for Turbojet and Turbofan Engine, NASA TN D-6552, 1972.
[12]Palmer, J. R. and Yan, C. Z., “TURBOTRANS--A Programming Language for the Performance Simulation of Arbitrary Gas Turbine Engines,” ASME 82-GT-200, 1982.
[13]Kurzke, J., A Program to Calculate Design and Off-Design Performance of Gas Turbines, GasTurb 7.0 Users Manual, 1996.
[14]Bathie, W. W., Fundamentals of gas Turbines, 2nd ed., John Wiley & Sons Inc., New York, 1996.
[15]Saravanamutto, H. I. H. and Maclsaac, B. D., “Thermodynamic Models for Pipeline Gas Turbine Diagnostics,” J. of Eng. for Power, Vol. 105, pp.875-884, 1983.
[16]Kurzke, J., “How to Get Component Map for Aircraft Gas Turbine Performance Calculations,” ASME Paper 96-GT-48, 1997.
[17]賴正權、夏筱明、潘彥良、陳光宏,“燃氣渦輪引擎壓縮器特徵分析與實驗模組建置之研究”,2001中華民國「燃燒學會/民航學會/航太學會」學術聯合會議論文集,第61-68頁,元智大學,桃園中壢,2001。
[18]陳光宏,“微小流量壓縮器操作特徵試驗模組建置之研究”,碩士論文,中正理工學院兵器系統工程研究所,桃園大溪,2002。
[19]潘彥良,“氣渦輪引擎壓縮器操作特徵與失速界限之理論研究”,碩士論文,中正理工學院兵器系統工程研究所,桃園大溪,2002。
[20]Attia, M. S. and Schobeiri, M. T., “A New Method for the Prediction of Compressor Performance Maps Using One-Dimensional Row-by-Row Analysis,” ASME Paper 95-Gt-434, Intl. Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas, 1995.
[21]Schobeiri, M. T., “Verlustkorrelationen Fur Transonische Kompressoren,” BBC-TN 87/20, 1987.
[22]Greitzer, E. M., “Surge and Rotating Stall in Axial Flow Compressors, Part I: Theoretical Compression System Model,” ASME Trans., J. of Eng. For Power, Vol. 98, pp190-198, 1976.
[23]Moore, F. K., “A Theory of Rotating Stall of Multistage Axial Compressors,” NASA CR-3685, 1983.
[24]Moore, F. K., “A Theory of Rotating Stall of Multistage Compressors, Part I, II, III,” ASME J. of Eng. for Power, Vol. 106, No. 2, pp.313-336, 1984.
[25]Moore, F. K. and Greitzer, E. M., “A Theory of Post-Stall Transients in Multistage Axial Compression Systems,” NASA CR-3878, 1985.
[26]Davis, M. W. and O’Brien, W. F., “A Stage-by-Stage Post-Stall Compression System Modeling Technique,” AIAA Paper 87-2088, AIAA/SAE/ASME/ASEE 23rd Joint Prop. Conf., San Diego, California, 1987.
[27]夏筱明、賴正權、文宏達、吳宏佑、鍾沛祥,“小型渦輪引擎軸流式壓縮器性能建立(I) ”,國防科技學術合作協調小組研究計劃成果報告,中正理工學院,桃園大溪,2003。
[28]http://sats.larc.nasa.gov/downloads/SATS.jpg
[29]http://www.grc.nasa.gov/WWW/AST/GAP/wi0697.htm
[30]http://mzak.webzdarma.cz/motory/williams/williams.php
[31]http://www.angelfire.com/ny/USAircraft/missiles/AGM86B.html
[32]http://www.wpafb.af.mil/museum/engines/eng58.htm
[33]MIL-E-5008B, “Military Specification-Engine, Aircraft, Turbojet, Model Specification for,” The Department of Defense, January 1959.
[34]Mattingly, J. D., Elements of Gas Turbine Propulsion, New York, 1987.
[35]http://www.turbinedesign.com/enginerefpage_4.htm
[36]Hunecke, K., Jet Engines-Fundamentals of Theory, Design and Operation, Motorbooks International Publisher Wholesalers, 4th ed., 1997.
[37]http://www.grc.nasa.gov/WWW/RT2001/5000/5810skoch.html
[38]http://www.designfoil.com/
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